Download or read book A Wind tunnel Investigation of a 4 foot diameter Ducted Fan Mounted on the Tip of a Semispan Wing written by Paul F. Yaggy and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of Effect of Ratio of Wing Chord to Propeller Diameter with Addition of Slats on the Aerodynamic Characteristics of Tilt wing VTOL Configurations in the Transition Speed Range written by Robert T. Taylor and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Full scale Wind tunnel Investigation of the Static Longitudinal and Lateral Characteristics of a Light Single engine Low wing Airplane written by James P. Shivers and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Transonic Wind tunnel Investigation of the Static Longitudinal and Lateral Aerodynamic Characteristics of a Proposed Hypersonic Glider with Several Booster Configurations written by Ralph P. Bielat and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low speed Wind tunnel Investigation of a Wingless Jet VTOL Transport Model written by Marion O. McKinney and published by . This book was released on 1959 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Characteristics of Propeller driven VTOL Aircraft written by Robert H. Kirby and published by . This book was released on 1961 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of the Aerodynamic Characteristics of a Model Representative of a Supersonic Fighter class Airplane with an External flow Jet augmented Flap in Low speed Flight written by William A. Newsom and published by . This book was released on 1959 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Full scale Investigation of the Aerodynamic Characteristics of a Model Employing a Sailwing Concept written by Marvin P. Fink and published by . This book was released on 1967 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been conducted in the Langley full-scale tunnel to determine the aerodynamic characteristics of a full-scale model employing a sailwing concept and having a wing aspect ratio of 11.5. The wing had a rigid leading-edge spar, rigid root and wing-tip ribs with a trailing-edge stretched between these ribs, and a fabric covering stretched between the leading and trailing edeges. The fabric of the sail maintained a smooth airfoil contour over the installed angle-of-attack range, but some rippling occurred at the trailing edge near the wing root as the wing stalled. The aerodynamic characteristics of the sailwing, in particular the maximum lift and maximum lift-drag ratio, compared favorably with those of conventional hard wings. A lateral-control device based on the wing-warp principle was effective at angles of attack below that for wing stall, but at angles near stall, the control effectiveness became low and nonlinear.

Download or read book Aerodynamic Characteristics of Twin propeller Deflected slipstream STOL Airplane Model with Boundary layer Control on Inverted V tail written by Richard J. Margason and published by . This book was released on 1968 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Data from a 0 16 scale V STOL Model with Direct lift and Lift cruise Jets written by Matthew M. Winston and published by . This book was released on 1969 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book A Transonic Wind tunnel Investigation of the Effects of Nacelles on the Aerodynamic Characteristics of a Complete Model Configuration written by Melvin M. Carmel and published by . This book was released on 1953 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Investigation of Effect of Yaw on Lateral stability Characteristics written by Isidore G. Recant and published by . This book was released on 1942 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Combinations of an NACA 23012 tapered wing and a circular fuselage having a wedge-shaped rear were tested in the NACA 7- by 10-foot wind tunnel to determine the effect of wing-fuselage interference on the lateral-stability of wing-fuselage interference on the lateral-stability characteristics. The model configurations represented a high-wing, a mid-wing, and a low-wing monoplane. For each configuration, tests were made with a partial-span split flap neutral and deflected 60 degrees and with and without a vertical tail. Tests of the fuselage alone and of the fuselage with the vertical tail were also made.

Download or read book Wind tunnel Investigation at High Subsonic Speeds of the Effect of Spoiler Profile on the Lateral Control Characteristics of a Wing fuselage Combination Winter Quarter chord Line Swept Back 32 6 and NACA 65A006 Airfoil Section written by Harold S. Johnson and published by . This book was released on 1953 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Investigation of the Effects of Leading edge Chord extensions and Fences in Combination with Leading edge Flaps on the Aerodynamic Characteristics at Mach Numbers from 0 40 to 0 93 of a 45 Degree Sweptback Wing of Aspect Ratio 4 written by Kenneth P. Spreemann and published by . This book was released on 1957 with total page 644 pages. Available in PDF, EPUB and Kindle. Book excerpt: This investigation was made to determine the effects of 6 degree full-span and 3 degree partial-span leading-edge flaps in combination with chord-extensions or fences on the aerodynamic characteristics of a wing-fuselage configuration with a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.3, and NACA 65A006 airfoil sections. The investigation was made in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.40 to 0.93 and an angle-of-attack range of about -2 degrees to 24 degrees. Lift, drag, and pitching-moment data were obtained for all configurations. From overall considerations of stability and performance it appears that with the model of this investigation the 6 degree full-span leading-edge flaps in combination with the chord-extension over the outboard 35 percent of the span, with or without leading-edge camber, would be the most desirable configuration.

Download or read book Full scale Wind tunnel Tests of a Small Unpowered Jet Aircraft with a T Tail written by Paul T. Soderman and published by . This book was released on 1971 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of a full scale executive type jet transport aircraft with a T-tail were investigated in a 40 x 80 ft (12.2 by 24.4 meter) wind tunnel (subsonic). Static, longitudinal, and lateral stability, and control characteristics were determined at angles of attack from -2 deg to 42 deg. The aircraft wing had 13 deg of sweep and an aspect ratio of 5.02. The aircraft was tested power off with various wing leading- and trailing-edge high lift devices. The basic configuration was tested with and without such components as engine nacelles, wing tip tanks, and empannage. Hinge-moment data were obtained and downwash angles in the horizontal-tail plane location were calculated. The data were obtained at Reynolds numbers of 4.1 million and 8.7 million based on mean aerodynamic chord. The model had static longitudinal stability through initial stall. Severe tail buffet occurred near the angle of attack for maximum lift. Above initial stall the aircraft had pronounced pitch-up, characteristic of T-tail configurations. A stable trim point was possible at angles of attack between 30 deg and 40 deg (depending on c.g. location and flap setting). Hinge-moment data showed no regions with adverse effects on stick force. Comparisons of wind-tunnel data and flight-test are presented.

Download or read book Transonic Aerodynamic Characteristics of a Variable sweep Airplane Configuration Having a 12 percent thick Wing and an Inboard Pivot Location written by Ralph P. Bielat and published by . This book was released on 1960 with total page 84 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind tunnel Investigation of the Aerodynamic and Structural Deflection Characteristics of the Goodyear Inflatoplane written by Bennie W. Cocke (Jr.) and published by . This book was released on 1958 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation has been conducted in the Langley full-scale tunnel to determine the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane over a range of test velocities from minimum stall speed up to speeds giving load factors for wing buckling. Tests were conducted over a range of speeds from approximately 41 to 70 mph with wing-guy-cable loads, wing-distortion photographs, and aerodynamic-force data recorded at each speed for a full range of angle of attack.